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In a nuclear photonic rocket, a nuclear reactor would generate such high temperatures that the blackbody radiation from the reactor would provide significant thrust. The disadvantage is that it takes a lot of power to generate a small amount of thrust this way, so acceleration, and, even with efficient nuclear fuel, specific impulse, are very low. The photon radiators would most likely be constructed using graphite or tungsten. Photonic rockets are technologically feasible, but rather impractical with current technology.
## Energy requirements and comparisons

The power per thrust required for a perfectly collimated output beam is 300 MW/N (half this if it can be reflected off the craft); very high energy density power sources would be required to provide reasonable thrust without unreasonable weight. The specific impulse of a photonic rocket is harder to define, since the output has no (rest) mass and is not expended fuel; if we take the momentum per inertia of the photons, the specific impulse is just c, which is impressive. However, considering the mass of the source of the photons, e.g., atoms undergoing nuclear fission, brings the specific impulse down to 300 km/s (c/1000) or less; considering the infrastructure for a reactor (some of which also scales with the amount of fuel) reduces the value further. Finally, any energy loss not through radiation that is redirected precisely to aft but is instead conducted away by engine supports, radiated in some other direction, or lost via neutrinos or so will further degrade the efficiency. If we were to set 80 % of the mass of the photon rocket = fissionable fuel, and recognizing that nuclear fission converts about 0.10 % of the mass into energy: then if the photon rocket masses 300,000 kg then 240,000 kg of that is atomic fuel. Therefore the fissioning of all of the fuel will result in the loss of just 240 kg of mass. Then 300,000/299,760 kg = an m_{i}/m_{f} of 1.0008. V_{f} = ln 1.008 × c where c = 300,000,000 m/s.
V_{f} then may be 240,096 m/s which is 240 km/s. The nuclear fission powered photon rocket may accelerate at a maximium of perhaps 1/10,000 m/s² (0.1 mm/s²) which is 10^{−5}g. The velocity change would be at the rate of 3,000 m/s per year of thrusting by the photon rocket. ## Power sources

Feasible current, or near-term fission reactor designs can generate up to 2.2 kW per kilogram of reactor mass. Without any payload, such a reactor could drive a photon rocket at nearly 10^{−4} m/s² (10^{−5}g; see g-force). This could perhaps provide interplanetary spaceflight capability from Earth orbit. Nuclear fusion reactors could also be used, perhaps providing somewhat higher power.## See also

## External links

If a photon rocket begins its journey in low earth orbit, then one year of thrusting may be required to achieve an earth escape velocity of 12.5 km/s if the vehicle is already in orbit at a velocity of 9,100 m/s, and 400 m/s additional velocity is obtained from the east to west rotation of the earth. The photon thrust will be sufficient to more than counterbalance the pull of the sun's gravity, allowing the photon rocket to maintain a heliocentric velocity of 30 km/s in interplanetary space upon escaping the earth's gravitational field. Eighty years of steady phontonic thrusting would be then required to obtain a final velocity of 240 km/s in this hypothetical case. At a 30 km/s heliocentric velocity, the photon ship would recede a distance of 600,000,000 miles (1 Tm) from the sun per year.

It is possible to obtain even higher specific impulse; that of some other photonic propulsion devices (e.g., solar sails) is effectively infinite because no carried fuel is required. Alternatively, such devices as ion thrusters, while having a notably lower specific impulse, give a much better thrust-to-power ratio; for photons, that ratio is $1/c$, whereas for slow particles (that is, nonrelativistic; even the output from typical ion thrusters counts) the ratio is $2/v$, which is much larger (since $vll\; c$). (This is in a sense an unfair comparison, since the photons must be created and other particles are merely accelerated, but nonetheless the impulses per carried mass and per applied energy—the practical quantities—are as given.) The photonic rocket is thus wasteful when power and not mass is at a premium, or when enough mass can be saved through the use of a weaker power source that reaction mass can be included without penalty.

A laser could be used as a photon rocket engine, and would solve the reflection/collimation problem, but lasers are absolutely less efficient at converting energy into light than blackbody radiation is—though one should also note the benefits of lasers vs blackbody source, including unidirectional controllable beam and the mass and durability of the radiation source.

A design proposed in the 1950s by Eugen Sänger used positron-electron annihilation to produce gamma rays. Sänger was unable to solve the problem of how to reflect, and collimate the gamma rays created by positron-electron annihilation; however, by shielding the reactions (or other annihilations) and absorbing their energy, a similar blackbody propulsion system could be created. An antimatter-matter powered photon rocket would (disregarding the shielding) obtain the maximum c specific impulse; for this reason, an antimatter-matter annihilation powered photon rocket could potentially be used for interstellar spaceflight.

- Application of nuclear photon engines for deep-space exploration by Andrey V. Gulevich, Eugeny A. Ivanov, Oleg F. Kukharchuk, Victor Ya. Poupko, and Anatoly V. Zrodnikov. AIP Conference Proceedings
- "Interstellar rendezvous missions employing fission propulsion systems," Lenard, R.X., and Lipiniski, R.J., in Proceedings of the Space Technology Applications Int'l Forum, 2000
- On the conversion of infrared radiation from fission reactor-based photon engine into parallel beam, Gulevich, A. V.; Levchenko, V. E.; Loginov, N. I.; Kukharchuk, O. F.; Evtodiev, D. A.; Zrodnikov, A. V., in Proceedings of the Space Technology Applications Int'l Forum, 2002
- Long-life space reactor for photon propulsion, Sawada, T.; Endo, H.; Netchaev, A., in Proceedings of the Space Technology Applications Int'l Forum, 2002

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